Orbital Minotaur V - Manual (Page 2)

Payload Accommodations
• Flight proven fairing shared with Minotaur IV
• Attitude controlled or spinning final stage
• Well defined environments from extensive flight data and well characterized
upper stages
• ISO 8 (100 k) to ISO 7 (10 k) cleanliness with temperature and humidity control
• Various flight-proven separation systems available, including low shock designs
Minotaur V
Performance
• Minotaur V has a GTO capability of 532 kg
- 185 km x 35786 km @ 28.5 degree
inclination, 180 AoP
• Minotaur V has a MTO capability at 39 degrees of
650 kg from CCAFS
- 185 km x 20,200 km at 39 Degree inclination,
180 AoP
• Minotaur V has a MTO capability at 55 degrees of
603 kg from WFF
- 185 km x 20,200 km at 55 Degrees
inclination, no AoP constraint
• Minotaur V has a TLI capability of 342 kg
C3 (km2/s2)
Pa
yl
oa
d (
kg
)
-60 -40 -20 0 20 40 60
1800
1600
1400
1200
1000
800
600
400
Minotaur V
Ø0.48 m
(19.2 in)
Ø1.33 m
(Ø52.5 in)
0.87 m
(34.5 in)
1.52 m
(60.0 in)
1.72 m
(67.7 in)
Ø38.81 in
Interface
(No Sep System)
Ø2.05 m
(Ø80.9 in)
Fairing Sep Plane
STAR 37
Inclination: 37.8˚
Direct Ascent
Perigee: 185 km
No Argument of Perigee Restriction
Secondary
Payload Volume
(Negotiable)
Copies of the Minotaur User's Guide
can be downloaded from:
www.orbital.com
Additional information should be obtained
from the USAF OSP Office
USAF SMC Space Development
and Test Directorate (SMC/SD)
Launch Systems Division (SMC/SDL)
Kirtland AFB, NM 87117-5778
(505) 853-5533 (505) 853-0507
For technical details or questions
please contact Orbital at:
[email protected]
Orbital Sciences Corporation
45101 Warp Drive • Dulles, Virginia 20166 • www.orbital.com
©2014 Orbital Sciences Corporation BR06006_2429